Turbine heater



June 23, 1953 J. H. EDWARDS 2,643,091

TURBINE HEATER Filed Feb; 11, 1950 4 Sheets-Sheet 1 WWW ATTORNEYS.

I June 23, 1953 J. H. EDWARDS 2,643,091

TURBINE HEATER Filed Feb. 11. 1950 4 Sheets-Sheet 2 INVENTOR.'

BY ATTORNEYS.

J- H. EDWARDS TURBINE HEATER June 23, 1953 4 Sheets-Sheet 3 Filed Feb. 11, 1950 M W f 2 W i W INVENTOR.

BY WWW ATTORNEYS.

.|., H. EDWARDS- TURBINE HEATER June 23, 1953 INVENTOR. dam

4 Sheets-Sheet 4 ATTORNEYS.

Filed Feb. 11, 1950 Patented June 23, 1953 UNITED STATES PATENT OFFICE TURBINE HEATER James H. Edwards, Evanston, Ill. Application February 11, 1950, Serial No. 143,757 3 Claims. (01. 253-79) This invention relates to a gas turbine which may be used. for the generation of both power and heat or for heating purposes only.

.The main objects of this invention are to provide an improved construction for a turbine wheel, and in particular; to provide an improved design and manner of mounting the individual blades on the rotor whereby the angular positioning of the first blade determines the angularity of and locks in place all the other blades.

In the embodiment shown in the accompanying drawings:

Fig. l is a side elevation of an improved turbine heater constructed in accordance with this invention;

Fig. 2 is a vertical, sectional elevation taken on the line 2-2 of Fig. 1;

Fig. 3 is an enlarged fragmentary, cross-sectional detail of the fuel and air mixing and igniting tube leading from the compression chamber to the expansion chamber; Fig. 4 is an enlarged fragmentary, crosssectional view of the auxiliary airinlet between the compression chamber and the expansion chamber;

Fig. 5 is an enlarged fragmentary View of the rotor showing the arrangement of the improved form of blades;

line 64 this invention, a portion of the housing being broken away to more clearly indicate the interior construction thereof.

A turbine heater constructed in accordance with this invention comprises a housing I partitioned and enclosed to provide co-axially located annular compression and expansion chambers II and I2, and mounting a blower I 3 and a turbine l4, and wherewith is associated a fuel supply and ignition equipment 15 and a valve controlled auxiliary air supply It between the compression and expansion chambers H and I2.

The housing I0 is of cylindrical form with radially and axially disposed partitions l1 and I 8 and end closures I9 and 20 forming the coaxial compression and expansion. chambers H and I2 and a dead chamber 2| inwardly of the expansion chamber l2. Attached to the housing l0 concentrically of the turbine I4 is a volute exhaust conduit 22 with its outlet 23.

The partition I l and the closure 19 mount a sets of bolts 36 and 37. through the inner radial casing part 32 into the tube 24 wherein is supported a bearing 25 for a shaft 26, whereon the impeller 21 of the blower l3 and the turbine M are secured in axially spaced relationship with the impeller 2'! located radially concentric with the compression chamber H and with the turbine rotor 28 located axially outwardlyof and adjacent to the expansion chamber l2.

The blower I3 comprises a casing 29, which, together with a plate 30 constitutethe closure for one end of the housing I 0 and within which casing is mounted the impeller 21.

As will be most clearly noted from Fig. 2. the casing 29 has an annular part 3| from the opposite ends of which extend the radially disposed parts 32 and 33. The annular part in its inner face is recessed at 34 in the plane of the en. cumference of the impeller 21 from which lead the tangential tubular discharge outlets 33.

As will, be further noted, most particularly from Fig. 2, the casing is secured in place by The bolts 36 extend partition ll, whereas the bolts 31 extend through the radially disposed casing part 33 into an internal flange or ears 38 formed on the housing Ill.

The plate is secured to the radially disposed casing part 33 by screws 39 and mounts a bearing 40 for the impeller 27.

The impeller 21 is of a rather conventional construction, being formed of a pair of plates 4| and 42 spanned by a series of vanes 43. The plate 4|, as herein shown, is disposed normal to the axis of the shaft 26 and has its hub 454 keyed to said shaft with a washer 44.! interposed between the face thereof and the end of the sleeve 24. The plate 42 is disposed at an incline normal to the shaft 26 and at its inner end is secured to a hub 45, which is journaled in the bearing 40. As most clearly shown in Fig. l, the vanes are disposed slightly inclined to the axis of the impeller 21. Air is drawn in through an inlet 46 formed by the hub and compressed and discharged peripherally through the tangential tubular discharge outlets 35 into the compression chamber II.

The turbine I4, as most clearly shown in Fig. 8, comprises the rotor 28 on which are arranged a circumferential series of blades or buckets 47, against which the gases from the expansion chamber l2 are directed through one or more nozzles 48. The rotor is secured to the shaft 26 by screws 49 extending through the hub of therotor into a flange 50 on said shaft. This shaft flange 50, incidentally, bears against a flange formed on the bearing 25, which in turn abuts flange 52 on the sleeve 24.

Bores 53 for the blades 48 are drilled in the rotor concentrically to and adjacent with its periphery, into which bores the blades 41 are press-fitted. As will be noted, from Fig. 5, the bores are each formed with a countersink 53.|.

The blades 41 are in the form of a crescent integral with a circular base or head 54 of the same diameter as the outer arc of the crescent and which is supported on a stud 55 smaller in diameter than the base 54, and such that the stud 55 will press-fit into a bore 53 in the rotor 28 with base 54 set into the respective countersink 53.I flush with the face of the rotor 28. The base 54 is formed with an arcuate shape recess 56 on the side opposite the crescent and on a radius equal to that of the base '56. As most clearly shown in Fig. 5, the recess 56 makes possible the locking of all of the blades 41 in the same angular disposition with respect to the rotor 28, which angularity is determined by the positioning of the first blade 41 set in a bore 53. 7

One axial edge of the crescent is cut away, as shown at 51, so that the distance to the next opposed blade is practically the same as the distance between the opposite edge of the crescent and the opposed face of the next adjacent blade. The edge which is cut away at 51 is on the opposite side of the nozzle 48 and provides against a possibility of a restriction in the discharge of the gases between the blades 41.

The general form and position of the nozzle 48 is most clearly indicated in Figs. 2, 5, and 8. Although a single nozzle is shown, it will, of course, be understood that several could be circumferentially arranged to direct gases from the compression chamber I2 against the blades 41.

The fuel supply and ignition equipment I5 comprises a pair of aligned tubes 58 and 59, with which is associated a fuel venturi 60, a fuel supply connection 6|, and a spark plug 62.

Although the tubes 58 and 59 are herein shown separate they might well be a single tube. However, as most clearly shown in Fig-3, the tube 58 is located in the compression chamber II and secured to the partition I1 by clamps 63 in axial alinement with the tube 59 extending into the expansion chamber I2. Heat dissipating ridges 64 are formed on the exterior of the tubes 58 and 59 so as to facilitate a dissipation into the respective chambers of the heat generated by the ignited gases in the tubes 58 and 59. An internal flange 58.I on the tube 58 serves to cause turbulence in the tube 58. The venturi 60 is formed in a bushing 65 located in the outer end of the tube 58. The fuel connection 6| is threaded into a bushing 66 mounted on the radially disposed part 33 of the blower casing 28. The connection 6| is provided with a bore 61 through which the fuel is introduced into the tube 58 through the venturi 60. The inner end of this connection 6| is tapered, as indicated at 68 and is connected to either a gravity or a pressure supply of fuel.

The spark plug 62 is threaded into a hub 69 radially of the tube 58 and connected to a suitable source of electricity.

The auxiliary air supply I6, as most clearly shown in Figs. 2 and 4, comprises a Venturi bushing 10 mounted on the housing partition I1 and controlled by a valve 1|. The Venturi bushing 10 is located between the annular part 3| of the blower casing 20 and the housing I0 4 at a point circumferentially removed from the fuel supply and ignition equipment I5, as is most clearly indicated in Fig. 1. The stem 1| is in turn threaded into a bushing 12 located in the radially disposed part 33 of the blower casing 20 with the end 13 of the valve exposed outwardly of the housing III to permit the turning of the valve 1| to adjust the air flow from the compression chamber II. through the Venturl bushing 10 into the expansion chamber I2.

An axially disposed partition 14 (see Fig. 1) extends radially across the expansion chamber [2 between the outer wall of the housing l0 and the axially disposed partition I8. This partition 14, as shown in Fig. 1 is located adjacent the auxiliary air supply I6 on the side thereof opposite the fuel supply and ignition equipment I5. This insures the auxiliary air supply being drawn past the end of the tube 59 by the burning gases moving toward and out through the nozzle 48.

Such an auxiliary air supply is provided so as to lower the temperatures of the burning gases in the expansion chamber I2 over what they would otherwise be and thereby make it unnecessary to construct this turbine heater from the more expensive higher heat resistant materials that have tobe provided for jet turbines used exclusively for power production purposes.

The exhaust conduit 22 would have its outlet 23 connected to any suitable conduit leading to the space to be heated, Where this device is to be used for heating purposes, or it would be open to the atmosphere were this device to be used for power purposes.

Obviously, some means would have to be provided to start the rotor 28 and maintain it in operation until the mixture in the tubes 58 and 59 was ignited and a sufficient pressure built up in the expansion chamber I2 sothat gases passing through the nozzle 48 could maintain the rotation of the rotor 28. This starter might be an electric motor such as is used for automobile engines.

The operation of the turbine heater herein shown is substantially as follows:

As just indicated, the rotation of the rotor would have to be initiated by a suitable selfstarter. As the impeller 21 revolves, air is drawn in through the opening 46, compressed between the vanes 43, and under increased pressure discharged tangentially out through the tubes 35 into the compression chamber I I. Here the compressed air is swirled through the chamber and enters the venturi 60, drawing with it fuel through the bore 61 of the fuel connection 6|. This mixture of air and atomized fuel is ignited by the spark plug 62 and directed through the tube 59 into the expansion chamber I2. The burning and expanded gases under compression in the expansion chamber I2 are discharged through the nozzle 48- against the blades 41 between which the gas passes into the volute conduit 22 and out through the outlet 23.

It will be noted that one of the tubes 35 is so positioned as to discharge a blast of air directly onto and across the end of the tube 58, which serves to facilitate the dissipation of heat generated therein.

As soon as the pressure of these gases through the nozzle 48 is sufficient, the rotation of the rotor 28 is maintained so long'as a supply of fuel is introduced through the connection 6| to the tube 58.

As temperature conditions indicate the necessity thereof, the valve H is adjusted so as to control a supply of auxiliary air through the venturi. 7!! from the compression chamber ll into the expansion chamber l2.

Variations and modifications in the details of structure and arrangement of the parts may be resorted to within the spirit and coverage of the appended claims.

I claim:

1. A turbine rotor comprising a disk having a series of evenly spaced, closely adjacent, countersunk, circular bores formed therein, with the centers of the bores equidistant from the center of the disk and with the axes of said bores parallel to the rotational axis of the disk, and turbine blades mounted in said bores, each turbine blade comprising a cylindrical stud portion fitted within its bore, a circular head portion fitted within the countersink of its bore, and a crescent-shaped blade integral with and risin from the head portion, each head portion having an arcuate slot formed in the periphery thereof with a radius equivalent to the radius of the head portion, the disk bores being spaced apart in amounts such that when adjacent blades are mounted in the disk, the head portion of any one blade fits within the arcuate recess of the next adjacent blade to thereby interlock said blades in fixed angular position with respect to the center of the disk.

2. A turbine blade comprising a cylindrical stud portion, a circular head portion and a crescent-shaped blade portion, the outer arcuate surface of the crescent-shaped blade portion being coextensive with the periphery of the head 6 3. A turbine rotor comprising a disk having a series of evenly spaced, closely adjacent, cir cular bores formed therein with the centers of the bores equidistant from the center of the disk,

and with the axes of said bores parallel to the rotational axis of the disk, and turbine blades mounted in said bores, each turbine blade comprising a cylindrical stud portion, a circular head portion, and a crescent-shaped blade portion, the outer arcuate surface of the crescent-shaped blade portion lying within the projected extension of the periphery of the head portion, and an arcuate recess formed in the head portion on the opposite side of the head portion from the blade portion, said arcuate recess having a radius equivalent to the radius of the head portion, each of said recesses interlocking with the adjacent head portion of the next adjacent blade, where= by any blade can be removed without disturbing any other blade, and all blades when in. place are firmly locked in a fixed angular position with respect to the center of the disk.

JAMES H. EDWARDS.

References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 799,062 Kerr Sept. 12, 1905 811,639 Holmgren Feb. 6, 1906 854,788 Wilson May 28, 1907 890,635 Fox June 16, 1908 986,317 Schmidt Mar. 9, 1911 1,986,435 Heinze Jan. 1, 1935 2,021,289 Caylor Nov. 19, 1935 2,028,603 Heinze Jan. 21, 1936 2,115,338 Lysholm Apr. 26, 1938 2,390,959 Pfenninger Dec. 11, 1945 

